• Title/Summary/Keyword: 부분분사터빈

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Experimental Investigation of the Effect of Partial Admission Ratio on the Performance of Supersonic Impulse Turbine (초음속 충동형 축류터빈의 부분분사비 효과에 대한 실험적 연구)

  • Jeong, Eun-Hwan;Park, Pyun-Goo;Kim, Jin-Han
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.4
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    • pp.59-66
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    • 2007
  • In this paper, experimental investigation results of the effect of partial admission ratio on the performance of axial turbine was presented. A supersonic impulse turbine of gas generator cycle liquid rocket engine turbopump was used for the test. for experimental purpose, a nozzle block, in which total 14 number of axi-symmetric convergent-divergent nozzles are arranged circumferentially, was designed and manufactured. Partial admission ratio was controlled by changing the number of active nozzles. High pressure air was used as working medium for the test. The experimental result revealed that the performance of the supersonic impulse turbine does not much affected by the partial admission ratio for supersonic impulse turbine.

A Study of the Second Stage Effect on a Partially Admitted Small Turbine (부분분사에서 작동하는 소형터빈에서 두 번째 단의 효과에 관한 연구)

  • Cho, Chong-Hyun;Cho, Bong-Soo;Choi, Sang-Kyu;Cho, Soo-Yong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.36 no.9
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    • pp.898-906
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    • 2008
  • A tested turbine consists of two stages, and an axial-type and a radial-type turbine are applied to the first and second stage, respectively. The mean diameter of the axial-type turbine rotor is 70 mm, and the outer diameter of the radial-type turbine is 68mm at the inlet. In this experiment, an axial-type turbine, two different radial-type turbines, and three different nozzle flow angles are applied to find the optimal design parameters. To compare the turbine performance, the net specific output torque is evaluated. The test results show that the nozzle flow angle on the first stage is a more important parameter than other design parameters for partially admitted small turbines to obtain high operating torque. For a 3.4% partial admission rate, the net specific output torque is increased by 13% with the addition of a radial-type rotor to the second stage when the turbine operates at $75^{\circ}$ nozzle flow angle.

Performance Prediction on a Partially Admitted Single-Stage Axial-Type Turbine (부분분사에 의하여 작동하는 축류형터빈의 성능예측에 관한 연구)

  • Cho Chong-Hyun;Cho Soo-Yong;Kim Soo-Yong;Choi Sang-Kyu
    • Journal of the Korean Society of Propulsion Engineers
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    • v.9 no.3
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    • pp.10-17
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    • 2005
  • A performance prediction model is developed for partially admitted axial-type turbines. Losses generated within the turbine are classified to the windage loss, expansion loss and mixing loss. The developed loss model is compared with an experimental result. The results predicted with the developed model agree well with the experimental results than those predicted with several other models because this model considers three different kinds of losses. Moreover, this model predicts well the performance even the partial admission is changed. So, this model could be applied to predict the performance of partially admitted axial turbine and it has a high accurate performance.

Performance Characteristics of a Partially Admitted Small Mixed-Type Turbine (부분분사에서 작동하는 소형 사류형 터빈에서의 성능특성에 관한 연구)

  • Cho, Chong-Hyun;Kim, Chae-Sil;Paeng, Jin-Gi;Cho, Soo-Yong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.9
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    • pp.889-898
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    • 2009
  • A mixed-type turbine was adopted and the rotor outer diameter was 108 mm. Turbine rotors were designed to the axial-type blade because the turbine operated at a low partial admission rate of 1.7-2.0% with two stages. Performance characteristics were studied when the spouting from the nozzle was toward radially inward or outward direction. Additionally, the effect at each stage of the rotor was measured. For comparing with each turbine performance, properties were measured based on various rotational speeds. Measured net specific torque was used to compare with the turbine system performance. On the mixed-type turbine, better performance was obtained when the operating air spouted toward radially inward direction. The specific torque was increased by 7.8% from using the second stage although its effect depended on the rotational speed.

A Study on Partial Admission Characteristics of a Multi-Stage Small-Scaled Turbine (다단 소형 터빈에서의 부분분사 특성에 관한 연구)

  • Cho, Chong-Hyun;Jeong, Woo-Chun;Kim, Chae-Sil;Cho, Soo-Yong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.9
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    • pp.943-954
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    • 2010
  • In this study, a radial inflow type turbine was applied and the outer diameter of the turbine rotor was 108 mm. The turbine blade on a circular plate disc was designed as an axial-type because its partial admission rate was 1.4-4.1%. The turbine consisted of three stages. The performance test has been conducted with various admission rates, tip clearances and nozzle flow angles. The turbine output power was measured on each stage. The turbine performance was obtained in a wide rotational speed range in order to compare its performance according to various operating conditions. The net specific output torque was also measured to compare its overall performance. Computational analysis was conducted for predicting turbine performance. The computed results were in good agreement with the experimental results.

Effect of Flow Angles at Nozzle and Solidities on a Partial Admitted Small Axial-Type Turbine (부분분사 소형 축류형터빈에서 현절비와 노즐유동각이 성능에 미치는 연구)

  • Cho, Chong-Hyun;Ahn, Kook-Young;Cho, Soo-Yong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.6
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    • pp.21-29
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    • 2008
  • Performance characteristics on a partially admitted small axial-type turbine are experimentally studied with changing design parameters, such as exit flow angles at the nozzle and solidities at the rotor. The tested turbine consists of a single-stage and its mean radius is 35 mm. In this experiment, three different solidities and four different nozzle flow angles are applied to find the optimal design parameter. For a comparison of the turbine performance, the net specific output powers are evaluated. For a 3.4% partial admission rate, the best performance is obtained when the rotor solidity is at 2.18, which is increased to 74% compared to the solidity at full admission.

Effect of Blade Angles on a Micro Axial-Type Turbine Operated in a Low Partial Admission Rate (부분분사 마이크로 축류형터빈에서의 익형각 효과에 관한 연구)

  • Cho, Soo-Yong;Cho, Bong-Soo;Cho, Chong-Hyun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.4
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    • pp.10-18
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    • 2007
  • A tested micro axial-type turbine consists of two stages and its mean radius of rotor flow passage is 8.4 mm. This turbine could be applied to a driver of micro power system, and its rotational speed in the unloaded state reaches to 100,000 RPM. The performance of this system is sensitive depending on the blade angles of the rotor and stator because it is operated in a low partial admission rate, so a performance test is conducted through measuring the specific output power and the net specific output torque with various blade angles on the nozzle, stator and rotor. The experimental results show that the net specific output torque is varied by 15% by changing the rotor blade angle, and the optimal incidence angle is about $10.3^{\circ}$.

Changes in Performance and Operating Condition of a Gas Turbine Combined Heat and Power System by Steam Injection - A Focus on Compressor Operation (증기분사에 의한 가스터빈 열병합발전 시스템의 성능과 운전조건 변화 - 압축기 작동 변화를 중심으로)

  • Kang, Soo-Young;Kim, Tong-Seop
    • The KSFM Journal of Fluid Machinery
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    • v.14 no.6
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    • pp.68-75
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    • 2011
  • This study simulated the effect of steam injection on the performance and operation of a gas turbine combined heat and power (CHP) system. A commercial simple cycle gas turbine was analyzed. A full off-design analysis was carried out to investigate the variations in not only engine performance but also the operating characteristics of the compressor caused by steam injection. Variation in engine performance and operation characteristics according to various operation modes were examined. First, the impact of full steam injection was investigated. Then, operations aiming to guarantee a minimum compressor surge margin, such as under-firing and partial steam injection, were investigated. The former and latter were turned out to be relatively superior to each other in terms of power and efficiency, respectively.

An Experimental Study of Surface Pressure on a Turbine Blade in Partial Admission (분사영역과 터빈익형 위치에 따른 표면압 변화에 관한 실험적 연구)

  • Choi, Hyoung-Jun;Park, Young-Ha;Kim, Chae-Sil;Cho, Soo-Yong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.39 no.8
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    • pp.735-743
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    • 2011
  • In this study, the distribution of surface pressure was measured in a steady state on a turbine blade which was moved the injected region and receded the stagnation region using a linear cascade apparatus. Axial-type blades were used and the blade chord was 200mm. The rectangular nozzle was applied and its size was $200mm{\times}200mm$. The experiment was done at $3{\times}10^5$ of Reynolds number based on the chord. The surface pressures on the blade were measured at three different nozzle angles of $58^{\circ}$, $65^{\circ}$ and $72^{\circ}$ for off-design performance test. In addition, three different solidities of 1.25, 1.38 and 1.67 were applied. From the results, the low solidity caused the low pressure on the blade suction surface at entering region and the reverse rotating force was generated at the low nozzle angle. The positive incidence also made the pressure lower on the suction surface at entering region.

Study on the Turbine Performance of 7 ton Liquid Rocket Engine Turbopump (7톤급 액체로켓 엔진 터보펌프 터빈 성능 연구)

  • Lee, Hanggi;Shin, Juhyun;Choi, Changho
    • Journal of Aerospace System Engineering
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    • v.11 no.1
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    • pp.8-13
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    • 2017
  • This study was performed to evaluate the turbine performance of a turbopump in the third stage engine of the Korea Space Launch Vehicle-II. The turbine is a supersonic impulse type with a single rotor. One nozzle is for starting and four remaining nozzles are for steady operation. A similarity test was carried out in the high air test facilities at the Korea Aerospace Research Institute. Test results showed that turbine efficiency changed much more from rotational speed variations than by pressure ratio variations. These results showed characteristics similar to other supersonic impulse turbines.